Gyroscope steering mechanism



Jan. 2, 1923,

1,440,822. w. DIETER.

.GYROSCOPE STEERING MECHANISM. FILED JULY 2,1919.

INVENTOR By Attorneys, 55mm. dun Q 4 m I 1918-, Serial No,'251,64.1.

ba ring;

Patented Jan. 2, 1923.

of Kings, city and uurrso STATES rajau'r OFFICE.

WILLIAM DIETER,

OF BROOKLYN, NEW YORK, ASSIGNOR TO VIT'ILEA DEVELOPMEN CORPORATION, ACORPORATION OF DELAWARE.

GYROSGOPE STEERING MECHANISM.

'? Application filed July 2, 1919. Serial No. 368,115.

.T 0 all whom it may concern:

Be it known that I, WILLIAM DInrER, a citizen. of the United States ofAmerica, residin in the boron h of Brooklyn, county S tate of New York,have invented certain new and useful Improvements in Gyroscope SteeringMechanism, of which-the following is a specification.

This invention relates togyroscopic steering mechanisms, such as areused for steering automobile torpedoes. In such mechanisms, thegyroscope is spun upeither by a spring motor or by the action ofcompressed air upon a turbine, this'spinning-up occurring while thetorpedo is still within the launching tube, or before it loses thedirection or aim given it by such tube. It is desirable to provide meansfor keeping the gyroscope spinning at a sufliciently high speed duringits run, and for this purpose the use of compressed alr at reducedpressure has been proposed.

the. present invention, the gyroscope is spun upby air at high pressure,being preferably the full initial pressure in the air flask, and ismaintained spinning by the turbine'efiect of jets of air at reducedpressure taken from any convenient source, preferably from the exhaustof one or both the servo-motors of the torpedo, as set forth in myapplication filed August 27,

According to The present invention provides certain improvements inconstruction, the nature and purpose of which will be developed as thedescription proceeds.

Referring to the accompanying drawings, which show. the preferredembodiment of the invention,

Figure 1 is a vertical section through the gyroscope box of a torpedo,the section bei mainly inthe plane of the outer g m- Fig. 2 is afragmentary horizontal section showing the parts at'the lower part ofFig. 1 mainly in elevation;

Fig. 3 is a transverse section on the line 3- -3 in Fig. 2;

Fig. 4 is a general view on a small scale, showing the connection withthe servo moi tors of the torpedo 5 is a fragmentary cross-section of Fithe f ywheel.

Fig. 6 is an enlarged cross-section of'one of the nozzles.

mer being Fig. 7 is an oblique elevation showing a floating bushing on amagnified scale.

For convenience, I will apply the same letters of reference as in mysaid prior application, so far as the parts are identical orsubstantially so.

E is the gyroscope case or box, within which is mounted in usual mannerthe g roscope J which'comprises the usual fly W eel a hung in a normallyhorizontal gimbal ring I), which in turn is hung on an axis at rightangles in an outer gim a1 ring 0, this ring being pivoted on a verticalaxis within a supporting framework of which the lower member is shown at(Z. The pivots comprise ball bearings of usual construction, and requireno special description.

High-pressure air is taken from the hig pressure side of the usualreducing valve,-

and conducted by a pipe 5 to the spinningup mechanism of the gyroscope,which is of. the usual construction, comprising a turbine g. F and H arethe servo-motors,

the horizontal steerin and the latter the depth engine. ir/at reducedpressure is taken through pipe m 'to the inlet valves of, these motors,and exhaust engine,

the forair from one or both motors is taken by a takenfrom thereservoir-t by .the usual manner as the seat for the cover 15 whichcloses the bottom opening through which the gyroscope may be reached.The opening 12 communicates with a duct 16 leading through the ring 13and terminatin a seat 17 which is preferably concave or the se ment of asphere, being ground to fit a simi arly shaped convex portion 18 formedat one 'end of a tubular member 19, which This for convenience I willcall a strutl strut hasat its opposite end a screw-20 having a conicalpoint 21 which enters a hole 22 suitably screwing out the pin 20. itpresses the cone s to an intermediate reservoir t, from which the air isconducted by a pipe it leadthe fly Wheel during a run of I I and is ledto an opening 12 in'av located in the ringj13, so that upon I I N thatjets from both shall impinge in the vex seatin face 18 against theconcave seat 17 and ma es a substantially air-tight joint. Withinthestrut 19 .is formed a duct 23 which leads to a point beneath thecentral bearing of the g roscope. The duct here is cone member of theball bearing attached to the gimbal ring 0 is drilled through centrallyto form a duct 29 which communicates with the duct 27, being alignedtherewith, and receives the jet of air therefrom. This duct 29.discharges into a lateral duct 30 drilled in the ring 0 and extending toboth sides, and communicating with oblique ducts 30' and vertical ducts31, the latter leading to the two ball bearings by which the inner ring6 is hung in the outer ring 0..

Each duct 31 is formed in a bearing member 32 and terminates in achamber 33 which is closed by a screw 34, the head of which screws upagainst a ring orgasket 35. In line with the screw 34 is a floatingbushing or loosely mounted cylindrical piston 36, shown separately inFig. 7, through which is a central bore forming a duct communicatingbetween the duct 31 and a duct formed centrally throughvthe cone of theball bearing which is fixed to the inner ring 6. Within this cone ismounted a nozzle piece 37 having on one side a hollow forming a chamberfor receiving the air, andon the other side an oblique jet orifice, asclearly shown in Fig. 1. This nozzle is shown on a magnified scale inFig. 6. The nozzles on opposite sides are precisely alike, but areinverted the one relatively to the other,- so

same rotative direction against the fly wheel. The fly wheel a isprovided with peripheral cross grooves 38 forming buckets to receive theimpingement of the jets. The shape of the fly wheel and of these groovesin. cross section, is shown in Fig. 5. The grooves are preferably abrupton both sides, being thus symmetrical in opposite ,rotary directions-,-

the fly wheel being thus reversible so that the fly wheel may beinserted. indifl'erently either way around, without affecting theoperation. The air from duct 31 communicates with the bore of piston 36by means of cross grooves in the end of the screw 34. The bushing orpiston 36. is made a free but close fit with the opening through whichit passes, and, receiving on its outer end the pressure of the air, isthereby caused to move inwardly, so that its inner end bears and byleakage, as otherwise the air would tend to escape through the ballbearing.- By this means a sufliciently close joint is provided withoutappreciable friction, since the air pressure employed is very moderate.

As compared with the construction set forth in my said formerapplication, the

present invention has the advantage of applying the air for maintainingthe fly wheel in rotation at points substantially coincident with thepivots of the inner ring, and consequently at points which cannot varyin their relation with the fly wheel, because, the fly wheel beingmounted in the inner ring, the latter accompanies the fly wheel in anytilting movement. It results that the jets for exerting the turbineeffect for maintaining the gyroscope in rotation, are applied to thebest advantage and without any disturbing reactions, their eifect beingthe same whether the gyroscope wheel is turning on a horizontal axis orupon an axis displaced therefrom to a Access to the gyroscope is readilyhad by removing the bottom cover 15 in the usual manner; thereupon,byturning the screw 20, the strut 19 canbequickly released and takenaway. This at once gives access to the duct 16 in the adapter ring 13,also to the ducts 27 and pivot. If the gimbal system is to be removed,the lower pivot frame d is taken out in the usual manner by removing itsscrews 40, of which one only is shown The several bored ducts are closedby'screw plugs 41, 42, which can be removed for cleaning in case ofnecessity. When the strut 19 is replaced,

the screwing up of the conical screw 20 forces the strut upwardly andthereby presses the gasket 24 against the nipple 28 to make an air-tightjoint.

The gaskets 35 limit the screwing in of the screws 34, while making anair-tight joint; the thickness of these gaskets should be such as tolimit the screwing in ofthe screws, so as to give just the required playto the floating bushings 36, and if this play is too much or too little,thinner should be substituted.

The floating bushings 36 should be precise duplicates, so as to presentthe same area to receive the pressureof the air, in order that they mayexert balanced pressures against orthicker gaskets 35 considerableangle.

29 in the lower gimbal the two ballbearing .conesatthe' inner ring.

The present construction is well adapted to a torpedo gyroscope which isadjustable for angle-fire. In such adjustment the box or shell E isrotated around a vertical axis which coincides with the axis of thepivotal mounting of the outergimbal ring 0, arranging the nipple28 andgasket 24 concentric with this axis, the turning communicating with saidpassages,

movement in adjusting for angle fire simply turns the nipple on thegasket, while pressing the air-tight connection between the ducts 23 and27. Y

It is not to be inferred from the detailed description given that theinvention is limited to the precise construction shown, it beingunderstood that it may be subject to a wide range of variation withinthe scope of the follow-ing claims. For example, the invention is notnecessarily limited to the duplication of the nozzles 37 whereby thegyro.- scope fly wheel is subjected to the balanced action of two likeair jets, although this provision is decidedly preferable.

On the whole, the construction provided by the present invention adaptsitself readily to the existing construction of the torpedo.

I claim as my invention 2-- i 1. In a gyroscope, in combination, innerand outer gimbal rings having fluid conducting passages thereincommunicating through the bearings thereof, a rotor journaled in one ofsaid rings, and fluid directing means, carried by one of said rings andcommunieating with said passages, for driving said rotor, located at abearing for packing the air duct against leakage. I

2. In a gyroscope, in combination, inner and outer gimbal rings havingfluid conducting passages therein communicating through the bearingsthereof, a rotor ournaled 1n one of said rings, and fluid directingmeans, carried by one of said rings and communieating with saidpassages, for driving said rotor, a bearing between said rlngs formed asa ball bearing ng, a cone on the other, and intervening balls, andpacking means bearing against said cone for preventing leakage where theduct asses through such bearing. v.

3. n a gyroscope, in combination, inner and outer gimbal rings-havingfluid conducting passages therein communicating through the bearin' 5thereof, a rotor journaled in one of sai rings, and fluid directingmeans, carried by one of said rings an for drlving said rotor, a bearingbetween said rings formed as a ball bearin in one ring, a cone on tvening balls, ing a member impingin the duct passing throng ing member.v j

4- A gyroscope comprising gimbal rings, with bearings connecting them,and a rotor, and driving means comprising ducts passing centrallythrough a bearing, and a floating bushing at such bearing receiving thepressure of the air on its outer end and making contact with an elementof the bearing on its inner end, avhereby the air pressure e other, andinteragainst such cone, the cone: and packand means responsive to airpressure, p

with a ball recess in one plied to the inner rin d to said rotor to witha ball recess j ,the rings receiving and packing means compnssuch nozzlepiece in its place.

impelled means fed therefrom for maintain-.

ing thdgyroscope in rotation, said means cqmprlsing a turbine nozzle,and an air duct entering from the exterior through avgimbal ring pivotto said nozzle, the parts traversed by said duct including a strutadapted at one end to seat against a fixed-part having a lateralopening, and a screw for pressing said strut into place adapted tosimultaneously make tight joints with the contacting arts containingportions of said duct.

7. In combination with a gyroscope, driving means comprising a turbinenozzle and a duct entering from the exterior to such nozzle through agimbal ring pivot, a strut through which a portion of such duct isformed, a connectingpart having a continuing part of said duct andmaking socket engagement with one end of said strut, and another parthaving a continuation of said duct, making lateral engagement with themiddle of said strut, and a cone screw for ressing said strut into placeadapted to thrust it both endwise and laterally to make: tight jointswith the continuing portions of saidduct.

8. In a gyroscope, the combination of outer and inner gimbal rings, anda rotor having journal bearings in the inner ring, fluid-conductingmeans passing through both rings and through a pivotal bearing betweensaid rings, and a circular-nozzle piece apin the axis of said pivotalbearing, forme with a jet orifice adjacent the axis, directedtangentially relative discharge 'a jet of fluid tan gentially againstits the gimbal ring having a clrcular recess concentric with the axis ofthe bearing between the nozzle piece. 9. A gyroscope comprising a rotorand inner and outer gimbal rings, a fluid passage through the bearingbetween said rings, the inner ring at said bearing having a smaller andlarger concentric recess, with a nozzle piece fitting the smaller recessand a bearing member fitting the larger recess and holding a In witnesswhereof, I have hereunto signed my name.

WILLIA DIETER,

peripheral portion, and

